Explosion turbine motor



June 1, 1943. G. H. wAKr-:FIELD EXPLOSION TURBINE MOTOR 1938 4Sheets-Sheet l Filed sept. 6

[NVE/WOR. GEORGE H. WAKEF/ELD A T TOR;

June 1, 1943- G. H. WAKx-:FiELD 2,320,391

EXPLOS ION TURBINE MOTOR Filed Sept. 6, 1938 4 Sheets-Sheet 2 June 1,1943.` G. H. WAKEFIELD 2,320,391

EXPLOSION TURBINE MOTOR Filed Sept. 6, 1958 4 Sl'urecs-Shea?l 3 Fmr/eusPLUG [NI/ENTOR.

GEORGE H. WAKE/75L D June 1, 1943 G. H. WAKEFIELD 2,320,391

EXPLOSION TURBINE MOTOR Filed Sept. 6, 1958 4 Sheets-Sheet 4 NVENTOR.GEORGE WAKEF/ELD Patented` June l, 1943 UNITED STATESv PATENT OFFICEEXPLOSION TURBINE MOTOR George H. Wakefield, Takoma Park, Md.Application September 6, 1938, Serial No. 228,667

30 Claims.

My invention relates to improvements in ex- PIOSOH turbine DOWer plants,stationary or nonstationary.

An object of the invention is to arrange and construct such power plantsthat a greater efficiency and economy in operation and a substantiallyprolonged life thereof is secured.

Another object of the invention is to provide means for eiiectivelycooling turbine blading, which is exposed to very high temperatures,Without appreciably reducing the temperature, the pressure, thevelocity, and the power of the combustion products.

In the operation of intermittent explosion type turbines, it isessential that certain fundamental difficulties be overcome before aturbine of this type will prove its superior efficiency and economy overthe present highly developed internal combustion engine. The first of`these difficulties arises from the fact that the temperature of theturbine blading must be kept within a safe range s as to not yburn theblades. At the same time, the temperature and pressure of the combustionproducts' shouldl be high in order to secure the desired economicaloperation of the turbine.

Many devices and arrangements have been proposed to overcome thesedifficulties, most of which having been proved to be only wasters ofheat and power. Early proposals involved the introduction of water or anexcess of air into the combustion products in the belief that thetemperature thereof would be sufficiently lowered and thus prevent anyburning of the blading. These proposals were also based upon the beliefthat the loss in power, due to the addition of water, would be offset bypower derived from the steam generated. This, however, has lnot provento be true. A later development, of spraying water into the nozzlepassages, during cylinder scavenging, has had the disadvantages ofprolonging the cycle, placing added drag on the blading t'hereby causingan appreciable co'oling of the succeeding hot charge, and involving amultiplied complicated and costly water-valve injector system.

I overcome these difficulties and disadvantages, first, by preferablyusing opposite directional rotating turbine blad'es, with alternatelayers revolving in opposite directions. Second, I introduce the coolingmedia, preferably water, into the path of the blades, `preferably at onepoint remote from the main power nozzles. In this way, every blade mustpass through the cooling zone and be cooled. The combustion productsmove through the blading in more or less straight lines and are very1ittle,if at all, effected by the cooling media which also moves throughthe blading in a like manner; the power nozzles and the cooling jetbeing separate and distinct one from the other..

By this means, the hot gases of combustion are expanded through theblading without coming into contact with the cooling media to anyappreciable degree and, if combustion gases are, to begin with, high intemperature even to the point of dis-association, they wi11 impart thegreatest amount of power possible. While the blading should remain aboutas h-ot as safety permits, excess heat imparted to it is quickly pickedup by the water, in the form of fine mist or steam. which is injectedfrom a suitable nozzle at` a speed akin to that of t'he combustionproductsfrom the power nozzles; the water, being transformed intosuper-heated steam on contact with the hot blading and already having ahigh velocity, acts as a source of high pressure steam power and,consequently, as an additional aid to the turbine. This is especially soWhere a booster gas or gases is employed to acceleratey t'he speed ofthe water spray.

With the foregoing advantages and objects, and others of equalimportance, in view, the inventionresides in the certain new and usefularrangement, combination and construction of parts, as will be hereaftermore fully described. set forth in the appended claims, and illustratedin the accompanying drawings, in which:

Figure 1 is a fragmentary side elevation, partly in section, of myimproved turbine and pump assembly and showing one means of cooling theturbine blading;

Figure 2 is a fragmentary end elevation of the turbine and showing amodied form of cooling means in assembly therewith;

Figure 3 is an enlargement of Figure 2 but with portions thereof brokenaway tosliow .features of the interior construction;

Figure 4 is a fragmentary longitudinal section taken on line 4 4 ofFigure 3;

Figure 5 is a fragmentary transverse section similar to Figure 3 butshowing yet another modified form of the cooling means;

Figure 6 is a vertical transverse section through a form of eccentricpump and showing its manner of application to the turbine in Figure 1;

Figure 7 is a vertical longitudinal section through a form ofself-cleaning, slow leak-return, check-valve as used in the assembliesof Figures 2, 3, and 5;

Figure 8. is vertical section through an automatic drain check-valve foruse at the bottom i Figure 12 is an end elevation of the cylinder` andvalve of Figure 11;

Figure 13 is a detail section of the latter valve per se;

Figure 14 shows an adaptation of the cooling system to an axial flowturbine in longitudinal section;

Figure 15 is a side elevation of the cooling jet valve as shown inFigures 2, 3, and 4, and showing a manually operated means therefor.

Referring to the accompanying drawings, wherein like characters ofreference designate corresponding parts throughout the several views,the constant volume combustion chambers are to be charged in anysuitable manner with fuel and compressed air, and the chamberintakevalve assemblies |8, I8', the power nozzles 63, 68, and the powernozzle valves 1| are arranged to deliver hot exploded charges from thecombustion chambers 20 into the turbine. The timing, the ignition, thecharging, and the charge control valve operating means may be any thatis common to the art and suitable for the purpose. As the hot highpressure intermittent charges enter the turbine, they come into contactwith the turbine blade sets 2|, 22, the blade set 2| being rotatable inthe opposite direction from that of the blade set 22. The blades 2|carried on a spindle 23 are bevelled opposite to -the blades 22 carriedon spindle 24. The spindles 23 and 24 are mounted securely onseparate'shafts 25 and 26, shaft 26 being solid and shaft 25 hollow tofit over shaft 26. 'I'he shafts 25 and 26 are free to revolve inopposite directions in suitable bearings 21 and relatively to theturbine housing 28, 29, in suitable bearings 30, 3|. 'Ihe shafts 25 and26 are carefully adjusted for radial and axial clearances by suitablethrust bearings and adjustments (not shown) common to the art. Gas leaksare kept to the minimum by suitable labyrinth packings 32, 33, spacebeing saved by putting the packing 32 over the exhaust ange 34 and thepacking 33 over the bearing 3|. Provision is made for escaping gases topass out of ports Y35 and not through bearing 3| The spindle 24 isformed with port openings 36 about its center for spent gases to escapeinto the exhaust pipe 31 through the exhaust fiange 34. ,y

A gear housing 38 is provided to enclose suitable reversing gears forthe shafts 25 and 26 and it may be supported separate from or secured tothe turbine housing 28 by any suitable means, such as bolts passedthrough flanges 46, 46'. Gear 39, which is secured to the outer turbineshaft 25, transfers motion to bevelled pinions 40 running loose onsuitable spindles 4|. Gear 42 is secured to the inner turbine shaft 26and is meshed with the pinions 40 for rotation in the direction oppositeto that of gear 39. A shaft 43 driven by one of the pinions 40 isavailable to operate any suitable ignition system, governor, or otherpart of the turbine. `A gear 44 is disposed' in mesh with a second setof bevelled pinions 40 within the housing 38 and like gear 39, reversesthe direction of rotation of another outer shaft 45 from that of shaft26 and it may be used to operate another similar turbine or othermachinery in conjunction with shaft 26'. The gearing and all bearingswithin the housing 38 may be packed with grease or oiled by any suitablelubricating system common to the art.

As the power charges pass from the combustion chambers 20 into theturbine, a portion of a charge is taken from one, or more than one', ofthe power nozzles 63 to operate a coolingliquid injection pump 41(Figure 1), a power nozzle 63 being ported as at 64 (Figure 3) for thepurpose. As shown in Figure 1, this charge is conducted by pipe 48 tothe pump 41. Due to the pulsating action of the exposion charges of thepower nozzles 63, the. piston 49 is moved to the right in cylinder 5|when the gas pressure is high and is forced to the left when the gaspressure is low by the action of a spring 52 against piston 50. Pistons49, 50, are made to operate as a unit. The amount of cooling liquidinjected is proportionate to the work of the turbine rather than to itsspeed. This is true because the work exerted on piston 49 by thecombustion gases varies directly in proportion with the work exerted bythe same gases on the turbine blading 2|, 22,

As the pistons 49, 50, move to the left by action of spring 52, Fig. 1,water is admitted or drawn into the cylinder 62 through check valve 53from pipe 54 leading from a water source (not shown), the check valve 55being closed. As the pistons 49, 50, are forced to the rightproportionately to the pressure of the charge in the power nozzle 63,check valve 53 closesA and the cooling .water is forced out past checkvalveA 55 through pipe 56 to a cooling jet 51 where it is sprayed as afine mist into the moving blading 2|, 22. The jet 51 may take many formscommon to the art. It is desirable, however, that the cooling water bebroken up sufficiently fine for good distribution through the blading2l, 22, as they pass through the cooling zone under the cooling jet 51.The jet 51 is secured to the turbine hous- -ing 28, 29, in much the sameway as are the power nozzles 63, 68, but separate and apart from them.The jet 51 and the power nozzles 63, 68, each occupy a different placeon the periphery of the turbine housing.

An adjusting screw 58, retarded by friction spring 59, is provided forregulating the tension on spring 52 which, in turn, regulates the amountof cooling liquid injected. The amount of the cooling liquid, as well asits pressure of injection, is also dependent on the ratio of the areawhich the driving piston 49 bears to the area of the driven piston 50,the size of the pipes 54, 56, ports, check-valves 53, 55, area of thecooling jet opening 51`and of the passages in the gas operating side ofthe pump 41, and it is to be here noted that the greater the force ofinjection of the water spray from jet 51, the less will be the drag onthe turbine blading 2|, 22; also, the greater will be its power`producing factor, especially when the water is hot and much or all of itis transformed -into superheated steam-upon contact with the blading. Itis obvious that due to the differential areas of the two pistons thewa*- ter pressure in cylinder 62 will be much greater than the gaspressure in cylinder 5|. The cylin- -der 5| is provided with a vent port6| for bleeding air from behind the piston 49.

In Figure 6, an eccentric pump 65 is shown connected to the liquidsupply pipe 54 to force jet 51. This pump will have the shaft 43 of itsrotor 65 geared' to thelturbine, as shown in Fig. 1 or otherwise driventherefrom, thereby causing the turbine blading 2|, 22, to be cooled bythe water spray proportionately to' the speed of the turbine and notproportionately to its load. This type of pump, or any other that isfound to be suitable, whether rotary, piston, turbine, or centrifugal,operating either singly or compoundly, may be interchanged with the gaspump 41 (Figure l), and they may be arranged to furnish in termittent orcontinual cooling of the blading 2 I,

22, and to eect proper coolingeither proportionately to the power loadof the turbine or to its speed, or both.

In Figures 2 to 4 and 7 to 10, both inclusive, a modified form ofcooling system is depicted and, although presenting a somewhat radicaldeparture in structure and operation, it is in reality but another formof automatic pump, with certain added functions. Here, a tank 66, toreceive a cooling liquid that is principally water, is secured on ornear the turbine, preferably between the power nozzles 63, 68, butremoved from them by the interposed cooling jet nozzle 61. The nozzlessupplying the combustion products from the combustion chambers 20 directto the turbine blading 2|, 22, are referred to as power nozzles 68 andthe nozzle, or nozzles as the case may be, tapped by -port 64 (Figure 3)as master power nozzle 63; one such master power nozzle being usuallysufficient. In the simplest form of the cooling means, as in Figure 1,thewater spraying terminus has been referred to as a cooling jet 51.Where the cooling jet 51 is assisted by gas pressure in the forcefulinjection of the cooling liquid, the chamber formed about the jet 51 ishereinafter referred to as the cooling jet nozzle 61.

The tank 66 may function on low pressures, but I prefer to operate it onthe high pressures of a combustion chamber 20. When the master powernozzle'valve 1| is open, it being controlled by a means 14 common to theart, the hot gases in making way into the turbine blading 2|, 22, exertconsiderable pressure on the port 64 and in pipes 12, 13, which carry aportion of the gases into the cooling jet nozzle 61 (pipe 12) and intothe top of the tank 66 (pipe 13). The pipe 13 delivers its portion ofthe gases into the tank 68 through a slow leak-return check valve 15.The introduction of gases to the top of the tank 66 exerts considerablepressure on the liquid therein, while the check valve prevents the gasesfrom returning to the master power` nozzle 63 and only allows them toleak off slowly after the turbine is stopped. The valve flap 89 (Figure7) is provided with a leak port 90 which, during the operation of thevalve, -is brought into engagement with a cleaningpin 9| projectinginwardly from the body. By this means the leakport is kept cleanautomatically throughout its operation.

The tank 66 is filled with water or other suit able cooling liquid. ThetopV of the tank 66 is preferably in the form of a removable cover orlid 92, while the side walls thereof may be so sloped as to preventdamage to the tank in the event of freezing of the cooling liquidtherein,

as will be well understood. The outside of the These exhaust gases passfrom the jacketed space about the tank out through a pipe 83 (Figure 3).The tank 66 may be further jacketed, as at 84, with the space betweenthe latter and the jacket 82, filled with a heat insulating material 85,in order that the cooling liquid or water within the tank will be keptnear a boiling ternn perature, or a temperature proportionate to itsgiven working pressure.l The size of the pipe 8| may be relied upon toregulate the heat imparted to the tank 66. The lower end of the tank 66may be extended to form the cooling jet 51 and provided with a removablevalve seat 93, as shown in Figure 5. The cooling jet nozzle 61(Figures'3, 4, and 5) may or may not be made as a unit Vwith the tank66.

As the turbine commences to run, the pressure in the tank 66 is quicklybuilt up; a portion of the combustion gases shooting through port 64,pipe 12 and cooling jet nozzle 61 each time a charge is deliveredthrough the master power nozzle 63 from its combustion chamber 20. Inpassing through the cooling jet nozzle 61 (Figures 3 and 4), the gasesstrike a pivoted depending flapper 94 within the cooling jet nozzle 61and force it into a more or less horizontally straightened position inrelation to the direction of gas flow. This movement of the flapper 94is proportionate to the magnitude of gas pulsations in the cooling jetnozzle 61, which pulsations are also proportionate to the load on theturbine because the magnitude of these gas pulsations varies in directproportion to the pressure in the power nozzles 63, 68, it beingunderstood that the air and fuel charges delivered to the combustionchambers 20 are in like manner varied with the load, Likewise is thepressure in tank 66 varied. This fiapper 94 has a rigid arm 96connecting it to a shaft 91 which is journalled in suitable bearings inthe walls of the cooling jet nozzle 61 and, when actuated, acts to openthe cooling jet valve 95 proportionately to the turbine load and thelatter, in turn, acts to admit an amount oi cooling liquid from the tankalso in proportion to the load. A packing nut 99 and a suitable packing(not shown) are provided to prevent escape of gas from the cooling jetnozzle 61 where the shaft 91 emerges from it. A spring |00 and a wingnut |0| provide the necessary adjustment for this automatic cooling jetnozzle assembly. The valve 95 (Figures 9 and 10) is secured on an arm96, forming a part of the flapper 94, by means of a lock screw |03,which also holds valve part |02 in place.

The water spray will reach both ends of the turbine blades 2|, 22, byreason of the shape of the cooling jet nozzle 61, Fig. 4, which expandsthe gases in proper manner along the axis of the blades as well asthrough the blade assemblies. This aids in keeping the cooling mediaseparate from the power gases as they both pass radially and side byside through the turbine. The power nozzles 63, 68, likewise may be ofthis flattened form to correspondingly shape the injected stream ofcombustion gases and thus eliminate need for ordinary'gas-directingbridges that are commonly employed and which easily overheat ciably aidin the operation of the turbine, while, at the same time, performing theimportant function of cooling the blading without interfer- 'ence fromor with the action of the power charges from the other of the combustionchambers 20.

I am aware that, by mixing water with a portion of the powergase's, aloss of power is incurred and this is true if any considerable amount ofthe combustion gases are utilized in force .feeding the cooling liquidin the stated manner.

However, the cooling jet nozzle 61 is preferably made quite small incomparison to the size of the power nozzles 63, 68, in order to minimizesuch loss and it is probable that thepower generated as steam by thevaporization of the cooling media will offset this loss. In any case,the amount of combustion gases so employed need not be such as togreatly impair the efficiency of the power plant.

The turbine housing sections 28, 29, are secured together in anysuitable manner, for instance, by bolts |05. The pipe 12, if need be,may be iinned, as shown in Fig. 5 or cooled in any usual manner. Also,the combustion chambers 20 and the power nozzle valves 1| may be cooledin any suitable manner, as by means of a water jacket |04, Figure 3. Afusible plug |06, Figure 4), is provided to blow out on overheating ofthe turbine and to give indication that the Cooling tank 66 is empty orthe system is in need of repair. Suitable lacings or rings |01 may besecured to the blade sets 2|, 22, in any suitable manner to lendstrength thereto and to allay vibration and their inner ends |08 arepreferably shaped to aid in directing the exhaust gases from the turbinehousing. A packing gland I9, Figure 4, is provided to prevent exhaustgases from entering the bearing 30.

The turbine assembly may be supported in op-l erative position by meansof brackets or the like |09. A check valve H0, Figures 3 and 8, isprovided in the bottom of the turbine housing for draining purposesshould there be a water leak into it in cold weather. This valve is madewith a slight tendency to open when the turbine is not running and toclose when it is in operation,

since any slight gas pressure in the housing 20, 29, causes it to close,while a spring I H forces it open when the pressure is relieved uponstoppage of the turbine. 'Ihe drain ports H2 in the casing of the valveI should be sufficiently large to remain clean.

In Figures 5, 11, 12 and 13, a modified form of cooling jet nozzle valveis shown. Here, a valve H3 is carried on an arm H4 and is held rmly on avalve seat 93 (Figure 5) by the tension of a spring I I5 disposed withina cylinder H6. The tension of this spring H5 is transferred through apiston rod H'I, an arm H8, and a shaft H9 to the arm I I4 and holds thevalve-I I3 on its seat to prevent any escape of the cooling liquid fromthe tank 6B when the turbine is notrunning. When the turbine is startedand gas pressure is built up in the pipe line 13, due to the action ofthe slow leak-return check valve as previously explained, a portion ofthis pressure passes from pipe 'I3 and enters a pipe |20 and acts upon apiston 2| to force it to the left within the cylinder H6; the motion ofthe piston being transferred through pistonrod ||1, the arm H8, and theshaft H9 and from the latter by way of the arm H4 to the valve H3. Thisaction leaves the cooling jet 51, Figure 5, wide open and it immediatelybegins to discharge water into the cooling jet nozzle 61 and hence intothe blading 2|, 22. The valve H3' is held open and at rest on anothervalve seat |23, when pressure in the line |20 and the cylinder H6 forcesthe piston |2| to the left, and thus prevents water and the gases ofcombustion from entering a casing |24 which encloses the valve arm I I4.A packing nut |25. Figure 12, is a further aid to prevent leakage aboutthe shaft H9 where it emerges from the casing |24. A suitable bracket|26 supports the cylinder H6 on the casing |24 or on the cooling jetnozzle 61, Figure 5. The valve H3 is secured to the arm H4 by a bushing|21 (Fig. 13) 'and is fitted suillciently loose on the arm to seatproperly on both seats 93, |23. As long as the turbine operates, thepressure in the cylinder I6 overcomes the spring H5 and holds the valveH3 on its lower seat |23, but, 'when the turbine is stopped and thepressure leaks olf through the check valve 15, the action of the springH5 forces the valve H3 back on seat 93. A vent |26 prevents backpressure on the piston |2|'.

The cooling, thus obtained, is continuous in proportion to the load onthe turbine, because the pressure in the cooling tank 66 changes withthe turbine load. The pressure in tank 66 quite closely follows thepressure in the power nozzles 63, 68, due to the action of the slowleakage return check valve 15. The cooling arrangement just describedcan be applied to any turbine wherein suilicient space cany be hadbetween the power nozzles 68 for the cooling jet 51, or a cooling jetnozzle 61.

The axial flow turbine, Figure 14, which may be either horizontally orvertically disposed, may be readily equipped with my cooling system.Also, turbines wherein the gases pass through blading in irregularcourses, as well as those which operate on radial ow, either outwardlyfrom the center orinwardly from the circumference.

As shown in Figure 15, the cooling liquid control valve H3 may bemanually operated through the medium of a rod |53. When the rod is movedto the right, valve H3 closes the cooling jet 51, Figure 5, and when itis moved to the left the jet is opened and the valve seats on the lowervalve seat |23. A compression spring |54 is so compressed. between afixed pin |55 and a valve actuating arm H6 that it holds the valve rmlyon either of the seats 93 or |23.

Without further description, it is though.I that the features andadvantages of the invention will .be readily apparent to those skilledin the art, and it will of course be understood that changes in form,proportion and minor detalls of construction and arrangement may beresorted to without departing from the spirit of the invention or itsscope as claimed.

Having thus fully described my invention, what I claim is:

1. In a turbine having opposite directional rotating blading operated bythe impingement on said blading of products of combustion under pressureand at temperatures which, in the absence vof cooling, are harmful tosaid blading, means injecting cooling water through said blading along apath which is non-coextensive with the path of combustion gases throughsaid blading, said injecting means including a nozzle and a controlvalve therefor normally closed, and means for automatically opening saidvalve in response to pressure of the products of combustion when theturbine is in operation.

2. In a turbine operated by the lproducts of combustion under pressureand having opposite directional rotating blading, means continuouslyinjecting cooling water through said blading along a path which isnon-coextensive with the path of combustion gases through said blading,dissipation of heat from the combustion gases to the cooling water beingthereby prevented prior to their reaction on the blading, said pathsbeing directed in a similar manner through said blading so that thecooling Water will strike the hottest portion of theblading first.

3. In a turbine operated by the products of combustion under pressureand having opposite directional rotating blading,`4 means intermittentlyinjecting cooling water through said blading along a path which isnon-coextensive with the path of combustion gases through said bladingdissipation of heat from the combustion gases to the cooling water beingthereby prevented prior to their reaction on the blading said pathsbeing directed in a similar manner through said blading so that thecooling water will strike the hottest portion of the blading first.

4. Means for cooling the opposite directional rotating blading of anexplosive turbine comprising means for injecting cooling Water throughsaid blading along a path adjacent to but noncoextensive with the pathof combustion gases through said blading, dissipation of heat from thecombustion gases to the cooling water being thereby prevented prior totheir reaction on the blading, means utilizing a portion of saidcombustion gases to forcibly eject said cooling water from saidinjecting means said injecting means including a nozzle and a controlvalve therefor normally closed, and means for automatically opening saidvalve in response to pressure of the products of combustion when theturbine is in operation.

5. Means for cooling the opposite directional rotating blading of anexplosive turbine, comprising means for injecting cooling water throughsaid blading along a path adjacent to but noncoextensive with the pathof combustion gases through said blading, dissipation of heat from thecombustion gases to the cooling Water being thereby prevented prior totheir reaction on the blading means regulating the rate of flow of saidcooling water from said injection means in accordance with the load onsaid turbine said injecting means including a. nozzle and a controlvalve therefor normally closed, and means for automatically opening saidvalve in response to pressure of the products of combustion when theturbine is in operation.

6. Means for cooling the opposite directional 4 rotating blading ofl anexplosive turbine, cornprising means for injecting cooling Water throughsaid blading along a path adjacent to but noncoextensive with the pathof combustion gases through said blading, dissipation of heat from thecombustion gases to the cooling water being thereby prevented prior totheir reaction on the blading said paths being directed in a similarmanner through said blading so that the cooling Water will strike thehottest portion of the blading first, and means supplying pressure tosaid cooling Water passing through said injecting means in proportion tothe load on said turbine.

7. Means for cooling the opposite directional rotating blading of anexplosive turbine having an explosion chamber, comprising means forinjecting cooling water through said blading along a path adjacent tobut non-coextensive with the path of combustion gases through saidblading, dissipation of heat from the combustion gases to the coolingwater being thereby prevented prior to their' reaction on the blading,said paths being directed in a similar manner through said blading sothat the cooling water will strike the hottest portion of the bladingrst and means supplying pressure to said cooling water lpassing throughsaid injecting means, intermittently and in timed relation to theexplosions occurring in said explosion chamber.

8. Means for cooling the opposite directional rotating blading of anexplosion turbine, comprising means for injecting cooling water throughsaid blading along a path adjacent to but noncoextensive with the pathof combustion gases through said blading, dissipation of heat from.

the combustion gases to the cooling Water being l thereby preventedprior to their reaction on the blading said paths being directed in asimilai manner through said blading so that the cooling water willstrike the hottest portion of the blading first, and means supplyingpressure to said cooling water passing through said injecting means inproportion to the' speed of said turbine.

9. In combination, a turbine operated bythe products of combustion underpressure and having oppositely rotating blading and a cooling meanstherefor, said coolingjmeans comprising means for injecting coolingWater through said blading along a path adjacent to but substantiallynon-coextensive Withthe path of combustion gases through said blading,dissipation of heat from the combustion gases to the cooling Water beingthereby prevented prior to their reaction on the blading said injectingmeans including a nozzle, a control valve which is normally held closedby resilient means, pneumatic means for opening said valve in responseto pressure of the products of combustion when the turbine is inoperation.

10. Means for cooling the opposite directional rotating blading of anexplosive turbine, comprising a tank for the storage of cooling Water, ajet for injecting said cooling Water through said blading along a pathadjacent to but non-coextensive with the path of combustion gasesthrough said blading, dissipation of heat from the combustion gases tothe cooling water being thereby prevented prior to their reaction on theblading and means supplying pressure to said tank for forcibly ejectingsaid cooling Water from said jet.

11. Means for cooling the opposite directional rotating blading of anexplosive turbine having a combustion chamber, said means comprising atank for the storage of cooling water, a jet for injecting said coolingwater through said blading along a path adjacent to but non-coextensivewith the path of combustion gases through said blading, dissipation ofheat from the combustion gases to the cooling water being therebyprevented prior to their reaction on the blading and means for supplyinga portion of said combustion gases to said tank for the forcefulejection of said cooling water from said jet.

12. Means for cooling the opposite directional rotating blading of anexplosive turbine having an intermittently red combustion chamber, saidmeans comprising a tank for the storage of cooling Water, a jet forinjecting said cooling water through said blading along a path adjacentto but non-coextensive with the path of combustion gases through saidturbine, means for supplying a portion of said combustion gases to saidtank for the forceful ejection of said cooling water from said jet, andmeans retaining a, sufficient they entersaid blading.

amount of said gases in said tank to provide a substantially uniformpressure therein while said turbine is in operation.

13. Means for cooling the opposite directional rotating blading of anexplosive turbine having an intermittently fired combustion chamber,s'aid means comprising a tank for the `storage of cooling water, a jetfor injecting said cooling water through said blading along a pathadjacent to ation to provide a substantially uniform pressure 'rotatingblading of an explosive turbine, compris-" ing a source of cooling waterunder pressure, a jet for injecting said cooling water through saidblading, a valve closing said jet against the prestherein, but allowingthe dissipation of said gases from said tank upon cessation of theoperation of said turbine. Y

14; Means for cooling the opposite directional rotating blading of anexplosive turbine, comprising means for injecting cooling water throughsaid blading along a path adjacent to but noncoextensive with the pathof combustion gases through said blading, dissipation of heat from thecombustion gases to the cooling water being thereby prevented prior totheir reaction on the blading said paths being directed in a similar`manner through` said blading so that the cooling water will strike thehottest portion of the bladingr rst and means regulating the pressure ofsaid cooling water entering said blading to pressures greater than theentering pressure of said combustion gases.

15. Means for cooling the opposite directional rotating` blading of anexplosive turbine, comprising a tank for the storage of cooling water, ajet for injecting said cooling water through said blading said jethaving means to adjust the opening thereof, means supplying said tankwith a portion of said combustion gases at substantially their enteringpressure for the forceful ejection of said cooling water from said jet,said adjusting means utilizing a portion of said combustion gases toregulate the size of the opening of said jet.

16. Means forcooling the opposite directional rotating blading of anexplosive turbine, comprising a source of cooling water under pressure,an adjustable jet for injecting said cooling water through said bladingsaid jet having means to adjust the opening thereof, said adjustingmeans utilizing a portion of the combustion gases of said A turbine toregulate the amount of openingof said jet in proportion to the pressureof said gases as 17. Means for cooling the opposite directional rotatingblading of an explosive turbine, comprising a source of cooling waterunder pressure, a jet for injecting said cooling water through saidblading, and means utilizing a portion of the combustion gases of saidturbine to increase the velocity of said water after it leaves said jetin proportion to the pressure of said gases vas they enter said blading.

18. Means for cooling the opposite directional rotating blading of anexplosive turbine comprising a source of cooling water under pressure, ajet for injecting said cooling water through said blading, meansnormally maintaining said jet closed, and means utilizing a portion ofthe combustion gases of said turbine to open said jet upon the startingof said turbine and to maintain Said U0 ing, a combustion chamber forfurnishing prodsure of said source, a flapper so connected to said valveas to open it an amount proportional to movement of said apper, andmeans bleeding oir a portion of the combustion gases of said turbine anddirecting them against said flapper and around the cooling Water leavingsaid jet, whereby velocity of cooling water leaving said jet will varyinvproportion to the pressure of said combustion gases.

20. A turbine having oppositely rotating blading, a combustion gas jetfor supplying the operating fluid thereto and a cooling-water jet spacedcircumferentially from said gas jet but directed similarly thereto, forsupplying the cooling water to the blading dissipation of heat from thecombustion gases to the cooling water being thereby prevented prior totheir reaction on the blading.

21. A turbine having oppositely rotating blading, a combustion chamberfor furnishing products of combustion, a combustion gas jet forsupplying said products of combustion as the operating fluid to saidblading, a cooling-water jet spaced circumferentially from said' gas jetbut directed similarly thereto for supplying the cooling water to theblading, and a gas conduit supplying a portion of the products ofcombustion from the combustion chamber to the said coolingwater jet forspeeding up the Water jet to a speed comparative to that of theoperating fluid.

22. A turbine having oppositely rotating blading, a combustion chamberfor furnishing products of combustion, a.v combustion gas jet forsupplying said products of combustion as the operating fluid to saidblading, a cooling-water jetl -to that of the operating fluid, andcooling means for said conduit.

23. A turbine having oppositely rotating bladucts of combustion, acombustion gas jet for supplying said products of combustion as theoperating uid to said blading, a cooling-water jet spacedcircumferentially from said gas jet but directed similarly thereto forsupplying the cooling water to the blading, a gas conduit supplying aportion of the products of combustion from the combustion gas jet to thecooling-water jet for speeding, up the Water jet to a speed comparativeto that of the operating fluid, cooling means for said'conduit, a waterreservoir and a connection between said conduit and said reservoir tosupply pressurethereto in accordance with the combustion chamberpressure.

24. A turbine having oppositely rotating blading, a combustion chamberfor furnishing products of combustion, a combustion gas jet for sup- 'aportion of the products of combustion from the combustion chambers tothe cooling water jet for speeding up the water jet to a speedcomparative to that of the operating fluid, cooling means for saidconduit, a water reservoir, a connection between said conduit and saidreservoir to supply pressure thereto and a slow-leak check valve in saidconnection.

25. A turbine having oppositely rotating blading, a combustion chamberfor furnishing products of combustion, a combustion gas jet forsupplying said products of combustion as the operating fluid to'saidblading, a coolingwater jet including a water nozzle spacedcircumferentially from said gas jet but directed similarly 'thereto forsupplying the cooling water to the blading, a gas conduit supplying aportion of the products of combustion from the combustion chamber to the'cooling water jet for speeding up the water 'jet to a speed'comparative to that of the operating fluid, cooling means for said.conduit, a water reservoir, a connection between said conduit and saidreservoir to supply pressure thereto, a slow-leak check valve in saidconnection, a valve for said nozzle normally held-resiliently closed andpneumatic means valve in response to the pressure of the combustion gas.

for opening said f 'a cooling Water jet spaced circurnferentially fromsaid gas jet but directed 'similarly .thereto 26. A turbine havingoppositely rotating alternate blading, a combustion chamberIintermittently furnishing products of combustion, bustion gas jet forsupplying said products as the operatinguid to saidblading, acooling-Watery jet spaced circumferentially from.said\gas jetV butdirected similarly thereto for supplying the cooling water to theblading at a speed comparative to that of said operating fluid, a'pneumatically-operated water pump connected to supply water to saidwater jet and a gas conduit between the combustion gas jet `and saidpump for supplying gases thereto for operating it in response to thepressure impulses of the combustion gas.

27. A turbine having oppositely rotating alternate blading, a combustionchamber intermittently furnishing products of combustion, a combustiongas jet for supplying said products as the operating fluid to saidblading, a cooling-water jet including a nozzle spaced circumferentiallyfrom said gas jet but directed similarly thereto for supplying thecooling water to the blading, a gas conduit supplying a portion of saidproducts of combustion'froml the combustion gas jet to said coolingwater jet for speeding up the water jet to a speed comparativeto that ofthe operating fluid, a water reservoir, a connection between saidconduit and said reservoir to supply pressure a comsupplying water to itin response to the erating iiuid to said blading,

spaced circumferentially from said gas jet but for supplying the coolingWater to the blading at a speed comparative to that of said operatingfluid, a pneumatically-operated water pump connected to supply water tosaid water jet, a gas conduit between the combustion gas jet and saidpump for supplying gases thereto for operating combustion gas, and meansfor controlling the stroke of said pump.

29. A turbine having oppositely rotating alternate blading, a combustionchamber furnishing products of combustion, a combustion gas jet forsupplying said products of combustion as the opa cooling water jetdirected similarly thereto for supplying the cooling water to theblading, dissipation of heat from the products'of combustion to thecooling water being thereby prevented prior to their reaction on theblading, a turbine-operated water pump for said water jet.

30. A turbine having oppositely rotating alternate blading, a combustionchamber intermittently furnishing products of combustion, a cornbustiongas jet for supplying said products of combustion as the operating fluidto said blading, a cooling water jet spaced circumferentially from saidgas jet but directed similarly thereto for supplying the cooling fluidto the blading, a gas con'duitsupplying a portion of the products ofcombustion from the combustion gas jet to said cooling water jet forspeeding up the water jet to a speed comparative to that of theoperating fluid, a water reservoir, a connection between said conduitand said reservoir to supply pressure thereto in accordance with thecombustion gas pressure,

a slow-leak check valve in said connection, a L

jacket around said Water reservoir, means for supplying the exhaustgases from the turbine to said jacket and means for regulating saidsupply.

GEORGE H. W

pressure impulses of the

